US3724219A - Combination catalytic reactor and exhaust silencer for internal combustion engines - Google Patents

Combination catalytic reactor and exhaust silencer for internal combustion engines Download PDF

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Publication number
US3724219A
US3724219A US00145834A US3724219DA US3724219A US 3724219 A US3724219 A US 3724219A US 00145834 A US00145834 A US 00145834A US 3724219D A US3724219D A US 3724219DA US 3724219 A US3724219 A US 3724219A
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United States
Prior art keywords
partition
chamber
exhaust gas
compartment
perforations
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Expired - Lifetime
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US00145834A
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English (en)
Inventor
C Lemaitre
P Allard
J Laparre
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Individual
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Individual
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Publication of US3724219A publication Critical patent/US3724219A/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/32—Constructional parts; Details not otherwise provided for
    • F02K9/36—Propellant charge supports
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B1/00—Engines characterised by fuel-air mixture compression
    • F02B1/02—Engines characterised by fuel-air mixture compression with positive ignition
    • F02B1/04—Engines characterised by fuel-air mixture compression with positive ignition with fuel-air mixture admission into cylinder

Definitions

  • a device for securing a propellant grain in the combustion chamber of a propellant 'unit comprises a plate fast with the front end of the propulsion unit.
  • the front face of the propellant grain is fixed rigidly to the plate.
  • the propellant grain is secured to the plate by means? stud inenfbe rs engaging int?) openings formed adjacent the periphery of the plate and permitting expansion of the grain without engendering significant stresses.
  • a grid fast with the rear face of the grain and having a cylindrical bearing surface cooperates with a bore of the rear end'of the propulsion unit.
  • the present invention relates to a method and device for securing a solid propellant grain in its combustion chamber.
  • thesolid propellant grain is restrained in the rocket combustion chamber by means of more or less elastic wedging devices in order to allow for thermal expansion and damp the mechanical loads to a sufficient degree to maintain the integrity of the propellant grain.
  • the front face of the propellant grain is rigidly fixed to the front end of the combustion chamber, and the rear face of the grain is positively located yet allowed to slide in relation to the rear end of the combustion chamber, while at the same time retaining effective thermal protection of the lateral walls of the combustion chamber.
  • the subject device of this invention enables the propellant grain to expand or contract freely, whereby it is not subjected to large stresses notwithstanding the big difference between the coefficients of expansion of the grain and the chamber.
  • FIG. 1 is a sectional view of a rocket chamber having a solid propellant grain fixed therein;
  • FIG. 2 depicts on an enlarged scale the portion of the device contained within frame A of FIG. 1;
  • FIG. 3 is a section taken through the line IIIIII of FIG. 1;
  • F IG. 4 is a fragmental view in section through the line IV IV of FIG. 3.
  • a device for securing a cylindrical solid propellant grain 1 contained in a combustion chamber 2 of a propulsion unit of the kind used, for instance, for propelling a tactical missile. It must be possible for such a propulsion unit to be stored handled and fired at any temperature between -40C and 50 C. If the diameter of the grain 1 is in the region of 033 metre and its length about 1.50 metre, then its length will vary by approximately 20.5 mm and its diameter by approximately 6mm between the aforesaid temperature limits.
  • the front face and lateral surface of the grain l is coated with an inhibiting varnish 7.
  • an inhibiting varnish 7 In order to safety.
  • a systematic diametrical clearance is provided I between the grain 1 and the wall of the combustion chamber in order to permit free expansion of the solid propellant grain responsively to temperature variations.
  • the front face of the grain 1 is fixed against a metal plate 3 made fast with the front end of the propulsion unit by a nut 6. Adjacent its centre, the plate 3 is formed with an annular ridge 5 adapted to engage into a matching recess in the grain 1, thereby locating the latter with respect to the plate.
  • the diameter of the ridge 5 is preferably comparatively small so that the mechanical stresses resulting from the different expansions of the metal and the grain should remain small.
  • the major axes of the openings 15 extend radially with respect to plate 3 in order to permit unrestrained thermal expansion of the propellant grain in relation to the plate.
  • sectors 4 could be replaced by a continuous ring they are nevertheless to be preferred in order to facilitate securing of the grain and limit the thermal stresses.
  • Each stud 11 is formed with a shank the shape of which makes for easier restraining of the stud in the propellant grain through the use of a volume of inhibiting varnish 17 in the region of the grains periphery.
  • each stud 11 extends through the grid and receives a circlip 18 which keeps the grid in contact with the grain.
  • the studs are allowed to shift laterally within a lodging l9 machined in the grid.
  • a ring 13 of elastomer material is positioned around each stud 11 and located in a bore formed in grid 12. Clearance is provided between ring 13 and solid propellant grain l, and the purpose of this ringis to damp movements of the solid propellant grain.
  • Grid 12 is formed with an annular locating member constituting a bearing surface 20 which enables it to be positively located in a matching guide member or bore 9 formed in the rear endpart 8 of the propulsion unit.
  • the part 8 is made of the same material as the grid, whereby such positive location remains effective at all temperatures since the grid and the part 8 have the same coefficients of expansion.
  • Grid l2 slides over its locating means when the grain 1 becomes longer or shorter responsively to temperature changes.
  • a longitudinal clearance is provided to permit expansion over the desired temperature range.
  • the length of cylindrical portion 20 is calculated according to the variation in the length of the grain, in order to ensure that positive location remains effective even at the lowest design temperature.
  • a device for securing a solid propellant grain in a rocket motor chamber comprising:
  • a plate member secured to the front end of the rocket motor chamber and having openings embodied therein adjacent its periphery
  • annular locating member attached to the opposite end of the solid propellant grain
  • said plate member including a projecting annular portion thereon fitting to a matching circular recess in the front face of the solid propellant grain for positive location of the grain in relation to said plate member.
  • annular locating member is a grid comprising a cylindrical bearing surface, said matching guide member being formed by a bore of matching shape.
  • a device as claimed in claim 3, wherein said means for fixing the rear face of the solid propellant grain to said grid are stud members embedded in the solid propellant grain, a ring made of elastomer material being further interposed between each said stud member and said grid.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
  • Exhaust Gas After Treatment (AREA)
  • Portable Nailing Machines And Staplers (AREA)
US00145834A 1970-05-28 1971-05-21 Combination catalytic reactor and exhaust silencer for internal combustion engines Expired - Lifetime US3724219A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7019637A FR2087716A5 (fr) 1970-05-28 1970-05-28

Publications (1)

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US3724219A true US3724219A (en) 1973-04-03

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Family Applications (1)

Application Number Title Priority Date Filing Date
US00145834A Expired - Lifetime US3724219A (en) 1970-05-28 1971-05-21 Combination catalytic reactor and exhaust silencer for internal combustion engines

Country Status (4)

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US (1) US3724219A (fr)
DE (1) DE2117401B2 (fr)
FR (1) FR2087716A5 (fr)
GB (1) GB1346089A (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3916618A (en) * 1973-10-17 1975-11-04 Nippon Oils & Fats Co Ltd Holding device for holding a propellant grain in a combustion chamber
US4118928A (en) * 1973-07-12 1978-10-10 Thiokol Corporation Means for mounting solid propellant in a rocket motor
RU2453721C2 (ru) * 2010-09-22 2012-06-20 Федеральное государственное унитарное предприятие "Научно-исследовательский институт полимерных материалов" Вкладной твердотопливный заряд торцевого горения ракетного двигателя

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109976400A (zh) * 2018-12-17 2019-07-05 西安航天化学动力有限公司 固体发动机加压固化自动控制装置及控制方法

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1522111A (en) * 1924-02-16 1925-01-06 Franck-Philipson Axel Muffler for internal-combustion engines
US2545682A (en) * 1947-07-30 1951-03-20 Universal Oil Prod Co Exhaust gas silencer and pressure reducer with plural valved outlets
DE1088764B (de) * 1958-04-18 1960-09-08 Gen Motors Corp Katalytischer Abgasreiniger fuer Brennkraftmaschinen
US3025132A (en) * 1959-08-07 1962-03-13 American Cyanamid Co Method of oxidizing hydrocarbon constituents of exhaust gases
US3065595A (en) * 1960-05-09 1962-11-27 Wright W Gary Catalytic converter system for internal combustion engines
US3556735A (en) * 1967-06-23 1971-01-19 Jacobo Epelman Muffler adapted to purify the exhaust gases of internal combustion engines

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1522111A (en) * 1924-02-16 1925-01-06 Franck-Philipson Axel Muffler for internal-combustion engines
US2545682A (en) * 1947-07-30 1951-03-20 Universal Oil Prod Co Exhaust gas silencer and pressure reducer with plural valved outlets
DE1088764B (de) * 1958-04-18 1960-09-08 Gen Motors Corp Katalytischer Abgasreiniger fuer Brennkraftmaschinen
US3025132A (en) * 1959-08-07 1962-03-13 American Cyanamid Co Method of oxidizing hydrocarbon constituents of exhaust gases
US3065595A (en) * 1960-05-09 1962-11-27 Wright W Gary Catalytic converter system for internal combustion engines
US3556735A (en) * 1967-06-23 1971-01-19 Jacobo Epelman Muffler adapted to purify the exhaust gases of internal combustion engines

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4118928A (en) * 1973-07-12 1978-10-10 Thiokol Corporation Means for mounting solid propellant in a rocket motor
US3916618A (en) * 1973-10-17 1975-11-04 Nippon Oils & Fats Co Ltd Holding device for holding a propellant grain in a combustion chamber
RU2453721C2 (ru) * 2010-09-22 2012-06-20 Федеральное государственное унитарное предприятие "Научно-исследовательский институт полимерных материалов" Вкладной твердотопливный заряд торцевого горения ракетного двигателя

Also Published As

Publication number Publication date
GB1346089A (en) 1974-02-06
DE2117401A1 (de) 1971-12-09
FR2087716A5 (fr) 1971-12-31
DE2117401B2 (de) 1973-03-29
DE2117401C3 (fr) 1973-10-11

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